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http://dx.doi.org/10.5139/JKSAS.2002.30.8.120

Hot Fire Tests of the KSR-III Sub.(I) Engines  

Kim, Y.H. (한국항공우주연구원)
Kim, Y.W. (한국항공우주연구원)
Moon, I.Y. (한국항공우주연구원)
Ko, Y.S. (한국항공우주연구원)
Lee, S.Y. (한국항공우주연구원)
Ryu, C.S. (한국항공우주연구원)
Seol, W.S. (한국항공우주연구원)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.30, no.8, 2002 , pp. 120-125 More about this Journal
Abstract
In the preceding tests using the KSR-III Sub.(I) engines, it was observed that the heat resistant capability of the engines was not enough for the mission. So Sub.(I) Mod. engines were designed and tested. The Sub.(I) Mod. engines have three major design parameters - the arrangement of main injectors, the impinging angle of main injectors and thermal barrier coating. More than twenty experiments were carried on to evaluate engine performance and heat resistance capability with respect to design parameters. In this study, the test results are introduced. Analysing the result of Sub.(I) engine tests, it is found that decreasing the impinging angle, adopting the H-type arrangement(rather than radial type arrangement) and adopting the thermal barrier coating can increase heat resistance capacity substantially. Also, engine performance evaluation is conducted using specific impulse and characteristic velocity parameter. The results show that the performance variation is small(about 5%) and the performance is better in the case of radial arrangement. It is suspected that these phenomena are caused by the change of flame structure atomization mixing characteristic of sprays and the distortion of recirculation zone. Also from the low frequency instability point of view, it is observed that reducing the impinging angle and adopting the H type arrangement can increase the instability characteristics.
Keywords
Liquid rocket engine; Model engine; Engine test; Engine performance;
Citations & Related Records
Times Cited By KSCI : 1  (Citation Analysis)
연도 인용수 순위
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